Gas Turbine Engine Combustion, Emissions and Alternative Fuels

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RT0
MEETING
PROCEEDINGS
14
Gas Turbine Engine Combustion,
Emissions and Alternative Fuels
(la Combustion dans les turbomoteurs, les émissions et les
carburants de remplacement)
Papers presented at the Applied Vehicle Technology Pane1 (AVT} Symposium (organized by
the former AGARD Propulsion and Energetics Pane1 (PEP)), held in Lisbon, Portugal,
12-16 October 1998.
Published June 1999
Distribution
and Availability on Back Cover
RTO-MP-14
AC/323(AVT)TP/lO
NORTH
ATLANTIC
RESEARCH
TREATY
ORGANIZATION
AND TECHNOLOGY
BP 25, 7 RUE ANCELLE,
RT0 MEETING
ORGANIZATION
F-92201 NEUILLY-SUR-SEINE
PROCEEDINGS
CEDEX, FRANCE
14
Gas Turbine Engine Combustion,
and Alternative Fuels
Emissions
(la Combustion dans les turbomoteurs, les émissions et les carburants de
remplacement)
Papers presented at the Applied Vehicle Technology Pane1 (AVT) Symposium (organized by
the former AGARD Propulsion and Energetics Pane1 (PEP)), held in Lisbon, Portugal,
12-16 October 1998.
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Organization
(RTO) of NATO
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ii
Gas Turbine Engine Combustion, Emissions
and Alternative Fuels
(RT0 MP-14)
Executive Summary
NATO efficiency in the future Will depend largely on air superiority, long range deployment capacity
and rapid response both on land and at sea. The gas turbine engine Will remain the power source of
choice, and fuel efficiency, fuel availability and exhaust emissions Will drive its design. The combustor
is one of the crucial engine components and combustion system problems have traditionally
contributed to well over half of the engine service problems in most air forces. The symposium focused
on and addressed the key challenges for reducing fuel consumption, lowering emission levels and
burning alternative fuels as requirements concurrent with improved performance and operation.
Widening the narrow standards of today’s fuels offers a short term solution to scarcity but has
detrimental effects on combustor life and emission levels. New fuels, such as liquid hydrogen and
methane, offer some potential advantages but also pose new combustion problems. The contribution of
military engines to en-rissions is of major concert-r today and Will continue to be in the future. There are
additional requirements for military engines such as higher combustion temperatures which are needed
for superior efficiency but at the same time low exhaust temperatures and low exhaust volumes to
reduce the infrared signature. Operability (blow-out stability and wind milling re-ignition, throttle
response, etc.) must be enhanced as the aircraft flight envelope and manoeuvrability are expanded.
Component durability must be maintained in an increasingly adverse environment. Combustor design,
active control of flame stability, control performance and exhaust gas composition as well as operating
procedure optimisation are the aims. Tools for combustion simulation and experimental validation are
under continua1 elaboration to save on development and life cycle costs through better design.
Scientists and engineers met military and civil operators, and discussion concentrated on the
customer’s future needs and constraints. A review of current R&D activities and formulation of
specific research resulted from the Symposium, for which there is no known competing event.
Universities, government laboratories, industry and some agencies of the military services were
represented and presented their knowledge and advice. The correct makeup of participants was indeed
achieved. Al1 papers presented were of good quality and covered new advances in many important
areas.
Highlight topics for future AVT symposia in this field would seem to be as follows: gaseous and
particulate emissions at altitude, optical diagnostics at elevated pressures in near-real combustors, and
active combustion control a11of which cari crucially contribute to the military usefulness of engines.
LU
La combustion dans les turbomoteurs,
les émissions
et les carburants de remplacement
(RT0 MP-14)
Synthèse
L’efficacité des forces de I’OTAN à l’avenir dépendra largement de la supériorité aérienne, de la
capacité de déploiement à grande distance et de l’intervention rapide terrestre et maritime. Le
turbomoteur restera le propulseur de choix et sa conception sera guidée par des considérations
d’émission de gaz polluants, ainsi que par des questions de rendement et de disponibilité du carburant.
La chambre de combustion est l’un des composants clés du moteur et l’expérience montre que plus de
la moitié des problèmes d’entretien des moteurs, rencontrés par la majorité des forces aériennes sont
liés aux systèmes de combustion. Le symposium a privilégié les défis clés de la diminution de la
consommation du carburant, l’atténuation des niveaux d’émission de gaz polluants et l’utilisation de
carburants de remplacement en vue d’améliorer les performances et le fonctionnement des
turbomoteurs.
Bien que l’assouplissement des normes restrictives qui s’appliquent aux carburants modernes offre une
solution à court terme aux problèmes de pénurie, elle s’accompagne d’effets indésirables pour la durée
de vie des chambres de combustion et les niveaux d’émission de gaz polluants. Les nouveaux
carburants, tels que l’hydrogène liquide et le méthane, s’ils offrent quelques avantages possibles,
posent en même temps des problèmes nouveaux de combustion. La contribution des moteurs militaires
aux émissions polluantes est, et restera, un sujet de préoccupation majeur. En plus, les moteurs
militaires ont des caractéristiques spécifiques, à savoir, des températures de combustion élevées, pour
assurer une meilleure efficacité, avec en même temps des températures et des volumes de gaz
d’échappement moindres, pour permettre de réduire la signature infrarouge. L’exploitabilité (stabilité
en cas de surpression, réallumage en autorotation, réponse du moteur, etc.) doit être améliorée au fur et
à mesure de l’augmentation de la maniabilité et de l’élargissement des domaines de vol. Il s’agit
également de conserver la longévité des composants dans un environnement de plus en plus
contraignant. La conception des chambres de combustion, le contrôle actif de la stabilité de la flamme,
les performances en matière de contrôle, la composition des gaz d’échappement et l’optimisation de la
procédure d’exploitation sont les objectifs en vue. Les outils de simulation et de validation
expérimentale de la combustion sont en évolution permanente dans le but de réaliser des économies sur
les coûts de développement et de possession par l’amélioration de la conception.
Les scientifiques et les ingénieurs qui ont assisté à la réunion ont pu rencontrer des exploitants
militaires et civils et leurs discussions ont porté essentiellement sur les besoins futurs des clients et les
contraintes qui leur sont imposées. Le symposium, qui est, à notre connaissance, unique en son genre, a
permis de faire le point des activités de R&D actuelles et de formuler des projets de recherche
spécifiques. Les universités, les laboratoires gouvernementaux, les industries et les agences militaires
représentés ont exposé leurs connaissances et proposé des conseils. Du point de vue des participants, la
répartition était équilibrée. Toutes les communications présentées ont été de bonne qualité, couvrant de
nouvelles avancées dans bon nombre de domaines importants.
Les sujets présentant un intérêt particulier pour les futurs symposia AVT dans ce domaine pourraient
être : les émissions particulaires et gazeuses en altitude, le diagnostic optique aux pressions élevées
dans des chambres de combustion quasi-réelles, et la combustion active, ces sujets pouvant faire l’objet
de contributions déterminantes dans le domaine des moteurs militaires.
iv
Click inside the blue boxes or on the titles to view the corresponding section
Contents
Page
Executive
. ..
lu
Summary
Synthèse
iv
Theme/Thème
ix
Recent Publications
on Propulsion and Power Systems of the Former AGARD
and Energetics Pane1 and the RT0 Applied Vehicle Technology Pane1
Programme
Propulsion
X
xii
Committee
Reference
Technical Evaluation
by G.J. Sturgess
Report
T
K
Keynote Address
by J.S. Lewis
SESSION
1: GAS TURBINES
IN LAND,
Ground Vehicle Mobility Requirements.
by G. Khalil and J. Hitchcock
Meeting
SEA AND AIR APPLICATIONS
the Challenge
with Electric
Drives
Advances in a Gas Turbine System for Ship Propulsion
by M.L. Parker, P.K. MacLeod and M. Coulson
Technical Challenges Associated with the Development
by C.A. Van Erp and M.H. Richman
SESSION
II: LOW
EMISSION
1
2
of Advanced
Combustion
Systems
3
COMBUSTORS
Paper 4 withdrawn
Empirical
and Anchored Methodologies
for Controlling
by R.P. Pandalai, G.C. Hsiao and H.C. Mongia
Combustion
Dynamics
5
Paper 6 withdrawn
NO, Reduction by Lean Premixed Prevaporized Combustion
by Th. Ripplinger, N. Zarzalis, G. Meikis, C. Hassa and M. Brandt
7
Status of Catalytic Combustion R&D for the Department of Energy Advanced Turbine
Systems Program
by D. Fant, G. Jackson, H. Karim, D. Newburry, P. Dutta, K. Smith, D. Smith and R. Dibble
8
Measurement
of Spray/Acoustic
Coupling in Gas Turbine Fuel Injectors
by T.J. Anderson, D.W. Kendrick, J.M. Cohen and T.J. Rosfjord
9
SESSION
Soot and Radiation
III:
Modelling
by H.T. Brocklehurst,
COMBUSTION
MODELLING
in Gas Turbine
Combustion
- PART
1
10
Cbambers
J.B. Moss, C.D. Hurley and C.H. Priddin
A Novel Code for the Prediction
Simulator
of Transient
Flow
Field in a Gas Turbine
Combustor
11
by N. Selçuk and 0. Oymak
Reduced
Kinetic
Mechanisms
by A. Linan, M. Bollig,
Numerical
Effects
Simulation
for Modelling
LPP Combustion
12
in Gas Turbines
A.L. Sanchez and B. Lazare
of the Reactive
Flow
in a Tubular
Chamber
with
Detailed
Kinetic
13
by B. Zamuner, B. Bourasseau, C. Berat and H. Niemann
Kerosene Combustion
Mechanisms
Modelling
using Detailed
and Reduced
Chemical
by M. Cathonnet, D. Voisin, A. Etsouli, C. Sferdean, M. Reuillon,
P. Dagaut
Modelling
of a Lean Premixed
14
Kinetic
J.C. Boettner and
15
Combustor
by P.J. Coelho and P. Salvada
SESSION
Validation
and Application
by K. Prommersberger,
Optical
Diagnostics
IV: OPTICAL
of a Droplet
MEASUREMENTS
Evaporation
Mode1 for Real Aviation
Applied
to a Jet Diffusion
by C. Hassa, M. Carl, M. Frodermann,
Th. Schilling and Th. Doerr
17
Flame
and Prediction
of NO and NO2 Emissions
Performance
Sector
with
Optical
18
V: EMISSIONS
by T.J. Foster, C.W. Wilson, M. Pourkashanian
by A. Dopelheuer
16
T. Behrendt, J. Heinze, 1. Rohle, N. Brehm,
SESSION
of Engine
Fuel
P. Bouchardy, V.R. Katta and W.M. Roquemore
Experimental
Investigation
of an Axially Staged Combustor
Diagnostics
at Realistic Operating
Conditions
Influence
1
G. Maier and S. Wittig
by F. Grisch, B. Attal-Tretout,
Measurement
- PART
from
19
Aero Engines
and A. Williams
on Emission
Characteristics
Conditions
and Alternative
20
and M. Lecht
Modeling the Effects of Operating
Performance
and Emissions
Fuels on Gas Turbine
21
by W.P.J. Visser and S.C.A. Kluiters
In-Flight
Spectroscopie
Aircraft
Emission
Measurements
22
by H.W. Jentink and J.J.F. van Veen
SESSION
The Design
and Evaluation
by M.I. Wedlock,
VI: COMBUSTOR
of a Piloted,
DESIGN
- PART
Lean But-n, Premixed,
J.R. Tilston and R.E. Seoud
1
Prevaporised
Combustor
23
Advance Fuel Injection Strategies for High Performance
by S. Samuelsen and V. McDonell
Gas Turbine
24
Engines
25
Turbulent
Structure of Generic LPP Gas Turbine Combustors
by B. Lazaro, E. Gonzalez, J. Alfaro, P. Rodriguez and A. Lecuona
Paper 26 withdrawn
NO, Reduction in a Fuel Staged Combustor by Optimisation
the Residence Time
by N. Brehm, Th. Schilling, A. Mack and G. Kappler
of the Mixing
27
Process and
Paper 28 withdrawn
SESSION
VII:
IGNITION
PROCESSES
A Novel Technique for Predicting the Ignition Performance
Combustion
Chamber
by C.W. Wilson, C.G.W. Sheppard and H.C. Low
Caractérisation
flamme
(Characterisation
by C. Guin
des systèmes d’injection
of Autoignition
prémélangés
and Flashback
en auto-inflammation
in Premixed
Injection
et remontée
VIII:
DESIGN
Experiments
in a Small Gas-Turbine
Combustor
by A.L. Heyes, D. Jelercic and J.H. Whitelaw
IX: ACTIVE
AGARD Workshops on Active Combustion
by V. Yang and K.C. Schadow
2
at Atmospheric
Gas Turbine
Systems
34
Fuels
35
Systems
36
and Their Active Control
37
with Gas and Liquid
COMBUSTION
Control
Combustion Instabilities
in Low NO, Gas Turbines
by B.T. Zinn, T. Lieuwen and Y. Neumeier
Combustion
32t
33
Design
K.J. Young, S.B.M. Beck and
in the Design of Low Emissions
SESSION
- PART
in a LPP Combustor
The Use of Fluidics in Gas Turbine Combustion
by R.J. Woolhouse, J.R. Tippetts, M. Whiteman,
J. Swithenbank
FueUAir Preparation
by M.K. Razdan
30
31
COMBUSTOR
On the Analysis of Combustion Performance
Pressure
by P.M. Anacleto and M.V. Heitor
de
Systems)
Ignition Diagrams and Bifurcation
Maps
by F.P. Di Maio, G. Barbier-i and P.G. Lignola
SESSION
29
of an Aero Gas Turbine
CONTROL
for Propulsion
Active Control of Combustion Instability
in a Liquid-Fueled,
Low-NO, Combustor
by J.M. Cohen, N.M. Rey, C.A. Jacobson, T.J. Anderson and T.J. Rosfjord
t Paper not available at time of printing
vii
38
Adaptive Control of Aeroacoustic Instabilities
by M. Mettenleiter, E. Haile and S. Candel
with Application
to Propulsion
Systems
39
Application
of Active Combustion
Control to Siemens Heavy Duty Gas Turbines
by S. Hoffmann, G. Weber, H. Judith, J. Hermann and A. Grthmann
40
Optimization
of Active Control Systems for Suppressing Combustion
by J.G. Lee, B.-S. Hong, K. Kim, V. Yang and D. Santavicca
41
SESSION
Optical Measurements
by B.H. Krautkremer,
X: OPTICAL
MEASUREMENTS
Instability
- PART
2
of Jet-Mixing
in a Swirling Crossflow of a Combustion
M.M. Blomeyer and D.K. Hennecke
Chamber
42
Optical Measurements
of Spray Combustion in a Single Sector Combustor from a
Practical Fuel Injecter at Higher Pressures
by T. Behrendt, M. Frodermann, C. Hassa, J. Heinze, B. Lehmann and K. Stursberg
43
Combustion Characteristics
of a Trapped
by G.J. Sturgess and K.-Y. Hsu
44
SESSION
Vortex Combustor
XI: ALTERNATIVE
European Evaluation of JPS+lOO Fuel and Its Impact
by S.P. Bullock, A. Hobday and C. Lewis
FUELS
on Engine/Fuel
System Design
45
Paper 46 withdrawn
Catalytic Combustion
Concepts for Industrial
MegaWatt
by J.M. der Kinderen and R. van Yperen
Modification
of the Fuel Control
Hydrogen
by D. Dini
SESSION
XII:
Gas Turbines
System of a Gas Turbine
COMBUSTION
MODELLING
Numerical Predictions and Experimental
Turbine Combustors
by P. Di Martino and G. Cinque
Measurements
Soot Formation Modelling
in Turbulent
by P. Di Martino and G. Cinque
Diffusion
From MicroWatt
Engine
47
to
from Kerosene to
- PART
of Radiative
2
Heat Transfer
in Gas
Flames
Effkient Numerical
Calculation of Evaporating
Sprays in Combustion
by R. Schmehl, G. Klose, G. Maier and S. Wittig
48
49
50
Chamber
Flows
51
Paper 52 withdrawn
Pollutants Emission Prediction in Combustion
by 1. Malice, X.Y. Zhou and J.C.F. Pereira
in Inert Porous Media
“111
53
Theme
NATO efficiency in the future Will depend largely on air superiority, long range deployment capacity and rapid
response both on land and at sea. The gas turbine engine Will remain the power source of choice, and fuel
efficiency, fuel availability, and exhaust emissions Will drive its design. The symposium Will focus on the
combustor as the crucial engine component, and Will address the key challenges of reducing fuel consumption,
lowering emission levels, and buming alternative fuels. Widening the narrow standards of today’s fuels offers a
short term solution to scarcity but has detrimental effects on combustor life and emission levels. New fuels, such
as liquid hydrogen and methane, offer some potential advantages, but also pose new combustion problems. The
use of these fuels Will be considered, as Will the contribution of military engines to exhaust emission levels,
combustor design and operating procedures, and active control of flame stability. Development tools such as
combustion simulation and experimental validation Will also be discussed. Scientists and engineers Will meet
military and civil operators and discussion Will concentrate on the customer’s future needs and constraints. A
review of current R&D activities and formulation of specific research may result from the Symposium, for which
there is no known competing event.
Thème
L’efficacité, à terme, des forces de 1’OTAN dépendra en grande partie de la supériorité aérienne, ainsi que des
capacités de déploiement à grande distance et de réaction rapide sur terre et sur mer. Le turbomoteur restera le
propulseur de choix et sa conception sera guidée par des considérations de rendement énergétique, de
disponibilité de carburant, et d’émission de gaz polluants.
Ce symposium s’attachera à étudier la chambre de combustion en tant que composant propulsif fondamental et il
examinera les défis décisifs représentés par la diminution de la consommation de carburant, l’abaissement des
niveaux d’émission et les carburants de remplacement. Si l’augmentation
des normes actuelles qui s’appliquent
aux carburants peut fournir une solution à certains problèmes ponctuels de pénurie, elle a en revanche des effets
contraires sur la durée de vie des chambres de combustion et sur les niveaux d’émission. Les nouveaux
carburants, tels que l’hydrogène liquide et le méthane, offrent certes des avantages possibles, mais ils posent
aussi de nouveaux problèmes de combustion.
L’utilisation
de ces carburants sera étudiée, ainsi que l’apport des moteurs militaires aux problèmes des niveaux
d’émission des gaz d’échappement, aux procédures de conception et d’exploitation
et au contrôle actif de la
stabilisation de flamme. Les outils de développement, tels que la simulation de la combustion et la validation
expérimentale, seront également pris en compte. Des contacts seront établis entre scientifiques et ingénieurs
d’une part, et militaires et exploitants civils d’autre part, avec des échanges de vues sur les attentes futures des
utilisateurs et sur les contraintes qui leur sont imposées.
Le symposium, qui est le seul à être organisé sur ce sujet à l’heure actuelle, pourrait aboutir à une mise au point
des activités courantes de recherche et développement dans ce domaine, ainsi qu’à la formulation de projets
spécifiques de recherche.
ix
Recent Publications on Propulsion and Power
Systems of the Former AGARD Propulsion and
Energetics Pane1 and the RT0 Applied Vehicle
Technology Pane1
CONFERENCE
PROCEEDINGS
(CP)
Combustion and Fuels in Gas Turbine Engines
AGARD CP 422, June 1988
Engine Condition Monitoring
- Technology and Experience
AGARD CP 448, October 1988
Application
of Advanced Material for Turbomachinery
and Rocket Propulsion
AGARD CP 449, March 1989
Combustion Instabilities in Liquid-Fuelled
Propulsion Systems
AGARD CP 450, April 1989
Aircraft Fire Safety
AGARD CP 467, October 1989
Unsteady Aerodynamic
Phenomena in Turbomachines
AGARD CP 468, February 1990
Secondary Slows in Turbomachines
AGARD CP 469, February 1990
Hypersonic Combined Cycle Propulsion
AGARD CP 479, December 1990
Low Temperature
Environment
Operations of Turboenghtes
(Design and User’s Problems)
AGARD CP 480, May 1991
CFD Techniques for Propulsion Applications
AGARD CP 510, February 1992
Insensitive Munitions
AGARD CP 5 11, July 1992
Combat Aircraft Noise
AGARD CP 5 12, April 1992
Airbreathing
Propulsion for Missües and Projectiles
AGARD CP 526, September 1992
Heat Transfer and Cooling in Gas Turbines
AGARD CP 527, February 1993
Fuels and Combustion Technology for Advanced Aircraft Engines
AGARD CP 536, September 1993
Technology Requirements for Small Gas Turbines
AGARD CP 537, March 1994
Erosion, Corrosion and Foreign Object Damage Effects in Gas Turbines
AGARD CP 558, February 1995
Environmental
Aspects of Rocket and Gun Propulsion
AGARD CP 559, February 1995
LO~S Mechanisms and Unsteady Flows in Turbomachines
AGARD CP 571, January 1996
Advanced Aero-Engine
Concepts and Controls
AGARD CP 572, June 1996
Service Life of Solid Rocket Propellants
AGARD CP 586, May 1997
Aircraft Fire Safety
AGARD CP 587, September 1997
Future Aerospace Technology in the Service of the Alliance - Sustained Hypersonic Flight
AGARD CP 600, Volume 3, December 1997
Advanced Non-Intrusive
Instrumentation
for Propulsion Engines
AGARD CP 598, May 1998
MEETING
PROCEEDINGS
(MP)
Design Principles and Methods for Aircraft
RTA MP-8, February 1999
Gas Turbine
Engines
x
ADVISORY
REPORTS (AR)
The Uniform Engine Test Programme (Results of Working Group 15)
AGARD AR 248, February 1990
Test Cases for Computation
of Interna1 Flows in Aero Engine Components (Results of Working Group 18)
AGARD AR 275, July 1990
Test Cases for Engine Life Assessment Technology (Results of Working Group 20)
AGARD AR 308, September 1992
Terminology
and Assessment Methods of Solid Propellant Rocket Exhaust Signatures (Results of Working
Group 21)
AGARD AR 287, February 1993
Guide to the Measurement
of the Transient Performance of Aircraft Turbine Engines and Components (Results of Working
Group 23)
AGARD AR 320, Match 1994
Experimental
and Analytical Methods for the Determination
of Connected - Pipe Ramjet and Ducted Rocket Internal
Performance (Results of Working Group 22)
AGARD AR 323, July 1994
Recommended
Practices for tbe Assessment of the Effects of Atmospheric
Water Ingestion on the Performance
and
Operability
of Gas Turbine Engines (Results of Working Group 24)
AGARD AR 332, September 1995
Structural Assessment of Solid Propellant Grains (Results of Working Group 25)
AGARD AR 350, December 1997
CFD Validation for Propulsion System Components (Results of Working Group 26)
AGARD AR 355, May 1998
LECTURE
SERIES (LS)
Blading Design for Axial Turbomachines
AGARD LS 167, June 1989
Comparative Engine Performance Measurements
AGARD LS 169, May 1990
Combustion of Solid Propellants
AGARD LS 180, July 1991
Steady and Transient Performance Prediction of Gas Turbine Engines
AGARD LS 183, May 1992
Rocket Motor Plume Technology
AGARD LS 188, June 1993
Research and Development of RamlScramjets
and Turboramjets
in Russia
AGARD LS 194, December 1993
Turbomachinery
Design Using CFD
AGARD LS 195, May 1994
Mathematical
Models of Gas Turbine Engines and their Components
AGARD LS 198, December 1994
Integrated Multidisciplinary
Design of Higb Pressure Multistage Compresser Systems (LS-211)
published as RT0 EN 1, September 1998
AGARDOGRAPHS
(AG)
Measurement
Uncertainty within the Uniform Engine Test Programme
AGARD AG 307, May 1989
Hazard Studies for Solid Propellant Rocket Motors
AGARD AG 3 16, September 1990
Advanced Methods for Cascade Testing
AGARD AG 328, August 1993
REPORTS (R)
Application
of Modified LO~S and Deviation Correlations to Transonik Axial Compressors
AGARD R 745, June 1990
Rotorcraft Drivetrain Life Safety and Reliability
AGARD R 775, June 1990
Propulsion and Energy Issues for the 21st Century
AGARD R 824, March 1997
Impact Study on the use of JET A Fuel in Military Aircraft during Operations in Europe
AGARD R 801, January 1997
The Sit@e Fuel Concept and Operation Desert Shield/Storm
AGARD R 810, January 1997 (NATO Unclassified)
Active Combustion Control for Propulsion Systems
AGARD R 820, September 1997
xi
Programme
Committee
Programme
Committee
Chairman
Prof. R. Evans
Department
of Mechanical
Engineering
University
of British Columbia
2324 Main Mal1
Vancouver,
B.C. V6T lW5
Canada
BELGIUM
SPAIN
Prof. R. Jacques
Ecole Royale Militaire
30 avenue de la Renaissance
1000 Bruxelles
Prof. J. J. Salva Monfort
Dept. de Motorpropulsion
y
Termofluidodinamica
ETSIA
Plaza Cardenal
Ciseros
28040 Madrid
CANADA
TURKEY
Mr. D. Rudnitski
Head, Engine Laboratory
Institute
for Aerospace
Research
National
Research Council of Canada
Ottawa.
Ontario
KlA OR6
Dr. T. Yafar Katirçioglu
MSG ARGE D. Ba$anligi
06650 Yucetepe
Ankara
GERMANY
UNITED
Prof. D.K. Hennecke
Fachgebiet
Gasturbinen
Technische
Hochscbule
Petersenstrasse
30
64287 Darmstadt
und Flugantriebe
Darmstadt
Prof. Dr. P. Kotsiopoulos
Hellenic Air Force Academy
Chair of Propulsion
Systems
Dekelia, Attiki
UNITED
ITALY
e Applicate
NETHERLANDS
Prof. W. De Wolf
National
Aerospace
P.O. Box 153
8300 AD Emmeloord
Laboratory
PORTUGAL
Prof. M.N.R.
Nina
CTAMFUL
Instituto
Superior
Tecnico
Avenida
Rovisco Pais
1096 Lisboa Codex
Mr. R. Cottington
Research Manager
Propulsion
Technology
DERA Pyestock
Farnborough,
Hants,
Department
GU14
OLS
Prof. R.S. Fletcher
Deputy Vice Chancellor
Cranfield
Institute
of Technology
Cranfield,
Bedford
MK43 OAL
GREECE
Prof. G. Torella
Accademia
Aeronautica
Dipartimento
di Scienza
80078 Pozzuoli
(Napoli)
KINGDOM
al Vo10
STATES
Prof. F. Culick
California
Institute
of Technology
205 Guggenbeim
Mail Stop 205-45
Pasadena, CA 91125
Mr. R. Hi11
Chief of Technology
WLIPOT,
Building
18
1950 Fifth Street
Wright
Patterson
Air Force
Base, OH
Dr. C. Russo
Director
of Aeronautics
NASA Lewis Research Center
MS 3-8
21000 Brookpark
Road
Cleveland,
Ohio 44135
Dr. K. Schadow
Head, Propulsion
Research
Code 47420D, NAWCIWD
First Administration
Circle,
China Lake, CA 93555-6001
xii
Section
MS 104d
45433-7251
I
REPORT DOCUMENTATION
1. Recipient’s
2. Originator’s
Reference
References
3. Further
RTO-MP14
AC/323(AVT)TI’/lO
5. Originator
PAGE
ISBN
/
4. Security Classification
of Document
Reference
UNCLASSIFIED/
UNLIMIl-ED
92-837-0009-o
Research and Technology Organization
North Atlantic Treaty Organization
BP 25, 7 rue Ancelle, F-92201 Neuilly-sur-Seine
Cedex, France
6. Title
Gas Turbine
7. Presented
atkponsored
Engine Combustion,
Emissions
and Alternative
Fuels
by
the Applied Vehicle Technology Pane1 (AVT) Symposium (organized by the
former AGARD Propulsion and Energetics Pane1 (PEP)), held in
Lisbon, Portugal, 12-16 October 1998.
9. Date
8. Author(s)/Editor(s)
June 1999
Multiple
10. Author’siEditor’s
11. Pages
Address
616
Multiple
12. Distribution
Statement
There are no restrictions on the distribution of this document.
Information
about the availability
of this and other RT0
unclassified publications is given on the back caver.
13. Keywords/Descriptors
Gas turbine engines
Combustion
Combustion chambers
Fuel consumption
Exhaust en-rissions
Jet engine fuels
Aviation fuels
Availability
Alternative fuels
Aircraft engines
Performance evaluation
Research projects
Combustion efficiency
Combustion control
Mathematical
models
Computerized simulation
Optical measurement
Emission control
Design
Ignition
14. Abstract
The symposium dealt with Gas Turbine Engine Combustion, Emissions and Alternative Fuels.
Forty-six papers and a Keynote Address elucidated the role of the combustion process as a
crucial factor of engine performance and operability under various conditions including nonstandard, new fuels and environmental
effects of civil and military interest.
There were 12 Sessions covering the following
-
topics (some in 2 sessions):
Gas Turbines in Land, Sea and Air Applications
Low-Emission
Combustors
Combustion Modelling
Optical Measurements
Emissions
Combustor Design
Ignition Processes
Active Combustion Control
Alternative Fuels
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